Systems and methods for spraying fuel in an augmented gas turbine engine

ABSTRACT

In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application is a continuation of U.S. application Ser. No.17/166,477 filed Feb. 3, 2021, which is incorporated herein by referencein its entirety.

TECHNICAL FIELD

The technology relates generally to spraying fuel in an augmented gasturbine engine.

BACKGROUND

Generally, augmentor fueling schemes depend on spray bar and fuel systemdesign to achieve both core flow path fuel penetration and dispersion.Generating the required fuel zones to meet objectives for performance isin part a function of what fuel pressure ratio can be set and proximityof spray bars to another. Realizing these goals can affect the weight ofthe engine by sizing of the fuel pump and spray bar count.

BRIEF DESCRIPTION

Aspects and advantages of the present disclosure will be set forth inpart in the following description, or may be obvious from thedescription, or may be learned through practice of the presentdisclosure.

In an aspect of the present disclosure, a fuel spray apparatus forspraying fuel in an augmented gas turbine engine includes a spray barwith a fuel injection aperture to inject a fuel jet into a fuel conduit;the fuel conduit having a fuel window to discharge the fuel jet into acore exhaust flow of an augmented gas turbine engine; a first airflowconduit having a first orifice to discharge a first air stream into thecore exhaust flow; and a second airflow conduit having a second orificeto discharge a second air stream into the core exhaust flow, where thefirst orifice and the second orifice are paired with the fuel window tocooperatively shape the fuel jet coming out of the fuel window.

In another aspect of the present disclosure, a system for spraying fuelin an augmented gas turbine engine includes a gas turbine engine havingan augmentor portion for burning fuel; and at least one fuel spray barfor spraying fuel within the augmentor portion. In some embodiments, theat least one fuel spray bar includes a first spray bar with a fuelinjection aperture to inject a first fuel jet into a first fuel conduit;the first fuel conduit having a first fuel window to discharge the firstfuel jet into a core exhaust flow of the augmentor portion; a firstairflow conduit having a first orifice to discharge a first air streaminto the core exhaust flow; and a second airflow conduit having a secondorifice to discharge a second air stream into the core exhaust flow,wherein the first orifice and the second orifice are paired with thefirst fuel window to cooperatively shape the first fuel jet coming outof the first fuel window.

In another aspect of the present disclosure, a method for spraying fuelin an augmented gas turbine engine includes directing a fuel jet into acore exhaust flow of an augmented gas turbine engine via a fuel windowof a fuel conduit configured to receive the fuel jet from a fuelinjection aperture of a spray bar; directing a first air stream into thecore exhaust flow via a first orifice of a first airflow conduit; anddirecting a second air stream into the core exhaust flow via a secondorifice of a second airflow conduit, wherein the first air stream andthe second air stream cooperatively impinge the fuel jet into a shape asthe fuel jet comes out of the fuel window.

These and other features, aspects and advantages of the presentdisclosure and/or embodiments will become better understood withreference to the following description and appended claims. Theaccompanying drawings, which are incorporated in and constitute a partof this specification illustrate embodiments of the present disclosureand, together with the description, serve to explain the principles ofthe present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

Disclosed herein are embodiments of systems, apparatuses and methodspertaining to spraying fuel in an augmented gas turbine engine. Thisdescription includes drawings, wherein:

FIG. 1 is a partial cross-sectional illustration of an exemplaryaugmented gas turbine engine showing exemplary fuel spray apparatusesfor spraying fuel in accordance with some embodiments;

FIG. 2 is a simplified illustration of an exemplary fuel spray apparatusin accordance with some embodiments;

FIG. 3 is a perspective view of an exemplary fuel spray apparatus inaccordance with some embodiments;

FIG. 4 is a cross-sectional view of the exemplary fuel spray apparatusof FIG. 3 taken along line A-A of FIG. 3 in accordance with someembodiments;

FIG. 5 is a cross-sectional view of an exemplary paired fuel window-airorifices of the exemplary fuel spray apparatus of FIG. 3 as taken alongline B-B of FIG. 3 in accordance with some embodiments;

FIG. 6 is a cross-sectional view of an exemplary paired fuel window-airorifices of an exemplary fuel spray apparatus in accordance with someembodiments;

FIG. 7 is a cross-sectional view of an exemplary paired fuel window-airorifices of an exemplary fuel spray apparatus in accordance with someembodiments;

FIG. 8 is a cross-sectional view of an exemplary paired fuel window-airorifices of an exemplary fuel spray apparatus in accordance with someembodiments;

FIG. 9 is a top-down illustration of an exemplary fuel spray apparatusin accordance with some embodiments;

FIG. 10 is a simplified illustration of an exemplary fuel sprayapparatus in accordance with some embodiments;

FIG. 11 is a schematic illustration of a cross-section of the exemplaryfuel spray apparatus of FIG. 10 showing layer arrangements of conduitsand heat shield walls in accordance with some embodiments;

FIG. 12 is a cross-sectional view of an exemplary paired fuel window-airorifices of an exemplary fuel spray apparatus in accordance with someembodiments; and

FIG. 13 shows a flow diagram of an exemplary process of spraying fuel inan augmented gas turbine engine in accordance with some embodiments.

Elements in the figures are illustrated for simplicity and clarity andhave not necessarily been drawn to scale. For example, the dimensionsand/or relative positioning of some of the elements in the figures maybe exaggerated relative to other elements to help to improveunderstanding of various embodiments. Also, common but well-understoodelements that are useful or necessary in a commercially feasibleembodiment are often not depicted in order to facilitate a lessobstructed view of these various embodiments. Certain actions and/orsteps may be described or depicted in a particular order of occurrencewhile those skilled in the art will understand that such specificitywith respect to sequence is not actually required. The terms andexpressions used herein have the ordinary technical meaning as isaccorded to such terms and expressions by persons skilled in thetechnical field as set forth above except where different specificmeanings have otherwise been set forth herein.

DETAILED DESCRIPTION

Generally speaking, pursuant to various embodiments, systems,apparatuses and methods are provided herein useful for spraying fuel inan augmented gas turbine engine. In some embodiments, a fuel sprayapparatus for spraying fuel in an augmented gas turbine engine includesa spray bar with a fuel injection aperture to inject a fuel jet into afuel conduit; the fuel conduit having a fuel window to discharge thefuel jet into a core exhaust flow of an augmented gas turbine engine; afirst airflow conduit having a first orifice to discharge a first airstream into the core exhaust flow; and a second airflow conduit having asecond orifice to discharge a second air stream into the core exhaustflow, where the first orifice and the second orifice are paired with thefuel window to cooperatively shape the fuel jet coming out of the fuelwindow.

In some embodiments, a system for spraying fuel in an augmented gasturbine engine includes a gas turbine engine having an augmentor portionfor burning fuel; and at least one fuel spray bar for spraying fuelwithin the augmentor portion. In some embodiments, the at least one fuelspray bar includes a first spray bar with a fuel injection aperture toinject a first fuel jet into a first fuel conduit; the first fuelconduit having a first fuel window to discharge the first fuel jet intoa core exhaust flow of the augmentor portion; a first airflow conduithaving a first orifice to discharge a first air stream into the coreexhaust flow; and a second airflow conduit having a second orifice todischarge a second air stream into the core exhaust flow, wherein thefirst orifice and the second orifice are paired with the first fuelwindow to cooperatively shape the first fuel jet coming out of the firstfuel window.

In some embodiments, a method for spraying fuel in an augmented gasturbine engine includes directing a fuel jet into a core exhaust flow ofan augmented gas turbine engine via a fuel window of a fuel conduitconfigured to receive the fuel jet from a fuel injection aperture of aspray bar; directing a first air stream into the core exhaust flow via afirst orifice of a first airflow conduit; and directing a second airstream into the core exhaust flow via a second orifice of a secondairflow conduit, wherein the first air stream and the second air streamcooperatively impinge the fuel jet into a shape as the fuel jet comesout of the fuel window.

FIG. 1 is a partial cross-sectional illustration of an exemplaryaugmented gas turbine engine 100 showing exemplary fuel sprayapparatuses 102 for spraying fuel in accordance with some embodiments.In some embodiments, the augmented gas turbine engine 100 includes acenter body 110, a fan duct 108, a turbine portion 112, an augmentorportion 106, and one or more fuel spray apparatuses 102 as exemplifiedin FIG. 1. FIG. 1 generally illustrates the general area where one ormore of a fuel spray apparatus 102 may be placed in an augmented gasturbine engine 100. Additionally, the fuel spray apparatus 102 in FIG. 1is shown in a spray bar configuration. Those skilled in the art willrecognize that embodiments of a fuel spray apparatus 102 describedherein may be made/manufactured in various shaped configurations (e.g.,vane-shaped configurations, heat shield configurations, flame holderconfigurations). Additionally, those skilled in the art will recognizethat embodiments of a fuel spray apparatus 102 described herein may bevariously arranged/placed in the augmented gas turbine engine 100 and/orthe augmentor portion 106 complimenting the improved fuel zone coveragebrought on by the fuel spray apparatus 102 described herein withoutdeparting from the scope of the embodiments herein. In some embodiments,core exhaust flow 104 flows from the center body 110 towards the fuelspray apparatus 102 where a fuel stream from the fuel spray apparatus102 is injected into the core exhaust flow 104 and combusted. Inoperation, the combustion may be aided by a flame holder (not shown), toprovide additional thrust. Those skilled in the art will recognize thatother components and/or sections, such as an inlet guide vanes, a fan, acompressor, and a combustion chamber, to name a few, are not shown thatare generally included in an augmented gas turbine engine 100.

FIG. 2 is a simplified illustration of an exemplary fuel spray apparatus102 in accordance with some embodiments. In some embodiments, the fuelspray apparatus 102 of FIG. 2 corresponds to the fuel spray apparatus102 of FIG. 1. In some embodiments, the fuel spray apparatus 102includes one or more paired fuel window-air orifices 202. A paired fuelwindow-air orifices 202 includes a fuel window 520 and one or morecorresponding air orifices, such as a first orifice 508 and a secondorifice 510, as described herein and shown on FIGS. 2, 3, 5-10, and 12.In some embodiments, the fuel spray apparatus 102 includes a heat shieldbody 210 and the one or more paired fuel window-air orifices 202. Forexample, the fuel window 520, the first orifice 508, and the secondorifice 510 are defined in an external surface of the heat shield body210 and extend through the fuel conduit 506, the first airflow conduit516, and the second airflow conduit 518, respectively. In someembodiments, the fuel spray apparatus 102 includes one or more fuelspray inlets 114 to receive fuel discharged by the one or more pairedfuel window-air orifices 202. In some embodiments, a portion of the fuelspray apparatus 102 is enclosed in the fan duct 108. In someembodiments, the portion of the fuel spray apparatus 102 enclosed in thefan duct 108 includes at least one fan duct inlet 204 to receive fanair/bypass air 208. In some embodiments, portions of the fan air/bypassair 208 flowing in the fan duct 108 enters the at least one fan ductinlet 204. Remaining portions of the fan air/bypass air 208 flows aroundthe fan duct-enclosed portion of the fuel spray apparatus 102 tocontinue downstream of the fan duct 108. In some embodiments, the fuelspray apparatus 102 is secured to the fan duct 108 with one or morefasteners 206. Such fasteners may include, for example, bolts used for aflange, nuts, washers, to name a few. The fan air/bypass air 208 flowinginside the fan duct 108 and portions of the one or more fuel sprayinlets 114 shown inside the fan duct 108 are depicted as visible in FIG.2 for illustration purposes. They are enclosed by the heat shield body210 and generally not visible. Portions of the fuel spray apparatus 102that are enclosed inside the fan duct 108 are depicted as visible inFIG. 2 for illustration purposes. Once the fuel spray apparatus 102 isfastened to the fan duct 108, this portion of the fuel spray apparatus102 is generally not visible.

FIG. 3 is a perspective view of an exemplary fuel spray apparatus 102 inaccordance with some embodiments. In some embodiments, the fuel sprayapparatus 102 corresponds to the fuel spray apparatus 102 of FIG. 2and/or the fuel spray apparatus 102 of FIG. 1.

FIG. 4 is a cross-sectional view of the exemplary fuel spray apparatus102 of FIG. 3 as taken along line A-A of FIG. 3 in accordance with someembodiments. In FIG. 4, the heat shield wall 406 is a top layer forminga surface of the fuel spray apparatus 102. In some embodiments, the heatshield wall 406 provides protection/shielding to one or more spray bars502 of FIGS. 5-9 of the fuel spray apparatus 102 from the temperatureenvironment inside the augmented gas turbine engine 100. In someembodiments, a main airflow conduit 402 directs the fan air/bypass air208 to at least partially surround a spray bar 502 that directs fuel tothe one or more fuel apertures 504. In some embodiments, the at leastone fan duct inlet 204 of FIG. 2 defines an opening to the main airflowconduit 402 that directs the fan air/bypass air 208 to the first airflowconduit 516 and/or the second airflow conduit 518 of FIGS. 5, 6, and 8.In some embodiments, the first airflow conduit 516 and the secondairflow conduit 518 are defined from cavities through the heat shieldwall 406 that terminate at distal ends proximate to openings to the mainairflow conduit 402 as shown in FIG. 5. In some embodiments, theconduits, channels, cavities, openings, orifices of the fuel sprayapparatuses 102 described herein are manufactured using one or moretypes of manufacturing processes (e.g., 3D printing or additivemanufacturing, CNC machining, polymer casting, rotational molding,vacuum forming, injection molding, extrusion, and blow molding, to namea few).

FIG. 5 is a cross-sectional view of an exemplary paired fuel window-airorifices 202 of the exemplary fuel spray apparatus 102 of FIG. 3 astaken along line B-B of FIG. 3 in accordance with some embodiments. Insome embodiments, a paired fuel window-air orifices 202 includes a spraybar 502 with a fuel injection aperture 504 for injecting a fuel jet intoa fuel conduit 506. In some embodiments, the paired fuel window-airorifices 202 includes the fuel conduit 506 having a fuel window 520 todischarge the fuel jet into a core exhaust flow 104 of an augmented gasturbine engine 100. In some embodiments, the paired fuel window-airorifices 202 includes a first airflow conduit 516 having a first orifice508 to discharge a first air stream into the core exhaust flow 104. Insome embodiments, the paired fuel window-air orifices 202 includes asecond airflow conduit 518 having a second orifice 510 to discharge asecond air stream into the core exhaust flow 104. The first orifice 508and the second orifice 510 are paired with the fuel window 520 tocooperatively shape the fuel jet coming out of the fuel window 520. Atleast one of the benefits of shaping the fuel jet as it comes out of thefuel window 520 is to improve fuel zone coverage. Better fuel flowpenetration into the core of the augmented gas turbine engine 100 aswell as dispersion and atomization of the fuel are achieved by pairingone or more air orifices 508, 510 with the fuel window 520.

For example, in some embodiments, at least one of a first shape of thefirst orifice 508 or a second shape of the second orifice 510 mayinclude, for example, a circular shape, oval shape, rectangular shape,square shape, triangular shape, and/or trapezoidal shape, among othergeometrical shapes. In some embodiments, the first orifice 508 and/orthe second orifice 510 may be sized based on a predetermined and/ordesired fuel zone coverage, dispersion, and/or atomization of the fuel.In some embodiments, the first orifice 508 and the second orifice 510are substantially shaped and/or sized similarly and/or equally. In someembodiments, the first orifice 508 and the second orifice 510 aredifferently and/or distinctively shaped and/or sized. In someembodiments, the first orifice 508 is configured to discharge a firstair stream having a first angular range 514. In some embodiments, thesecond orifice 510 is configured to discharge a second air stream havinga second angular range 512. In some embodiments, the first angular range514 and the second angular range 512 are substantially the same. In someembodiments, the first angular range 514 is different and/or distinctfrom the second angular range 512. In some embodiments, the firstangular range 514 and/or the second angular range 512 comprise anangular range from 20 degrees to 90 degrees. In some embodiments, thefirst orifice 508 and the second orifice 510 are shaped, sized, and/orconfigured to have a particular angular range 512, 514 to achieve apredetermined and/or desired fuel zone coverage, dispersion, and/oratomization of the fuel.

In some embodiments, one of the benefits of having the main airflowconduit 402 run along a radial length of the fuel spray apparatus 102 isto cooperatively shape the fuel jet coming out of the fuel window 520.This may be achieved by supplying air to the first airflow conduit 516,the second airflow conduit 518, the first subchannel 802, the thirdsubchannel 804, the second subchannel 602, the fourth subchannel 604,the upstream gap 702, and/or the downstream gap 704. In someembodiments, another benefit of having the main airflow conduit 402defined along a radial length of the fuel spray apparatus 102 is toremove heat from the fuel spray apparatus 102 as air flows through thefuel spray apparatus 102 and out of the first airflow conduit 516, thesecond airflow conduit 518, the first subchannel 802, the thirdsubchannel 804, the second subchannel 602, the fourth subchannel 604,the upstream gap 702, and/or the downstream gap 704 as shown and/ordescribed in FIG. 8 below.

In some embodiments, a first centerline 522 of the first airflow conduit516 is at a first angle relative to a second centerline 526 of the fuelconduit 506. In some embodiments, a third centerline 524 of the secondairflow conduit 518 is at a second angle relative to the secondcenterline 526 of the fuel conduit 506. For example, during themanufacturing process, each of the first airflow conduit 516 and thesecond airflow conduit 518 along with the first orifice 508 and thesecond orifice 510 may be formed, molded, machined, and/or printed at aparticular angle relative to the second centerline 526 of the fuelconduit 506 to cooperatively shape the fuel jet coming out of the fuelwindow 520. In some embodiments, each paired fuel window-air orifices202 in the fuel spray apparatus 102 may be formed, molded, machined,and/or printed based on its location, position, and/or placementrelative to the core exhaust flow 104 in the augmented gas turbineengine 100. In some embodiments, the fuel window 520 is approximatelyequidistant from both the first orifice 508 and the second orifice 510.

In some embodiments, the centerline of the fuel window 520 isapproximately equidistant from both centerlines of the first orifice 508and the second orifice 510. In some embodiments, the first orifice 508is positioned substantially across from the second orifice 510 relativeto the fuel window 520. In one example, the centerlines of the fuelwindow 520, the first orifice 508, and the second orifice 510 areaxially aligned. In some embodiments, a shape of the fuel window 520 maybe geometrically shaped (for e.g., a circular shape, oval shape,rectangular shape, square shape, triangular shape, and/or trapezoidalshape, etc.). In some embodiments, the first airflow conduit 516 and thesecond airflow conduit 518 are configured to receive at least one ofbypass air or bleed air of the augmented gas turbine engine. In someembodiments, the bypass air is an air stream from a fan of the augmentedgas turbine engine 100 that bypasses the engine core of the augmentedgas turbine engine 100. In some embodiments, the bleed air is sourcedfrom a compressor bleed offtake and/or elsewhere on the augmented gasturbine engine 100.

In some embodiments, the corresponding one or more air orifices pairedwith the fuel window 520 are defined in one or more openings to the fuelconduit 506 as shown in FIG. 6. FIG. 6 is a cross-sectional view of anexemplary paired fuel window-air orifices 202 of an exemplary fuel sprayapparatus 102 in accordance with some embodiments. In some embodiments,the first airflow conduit 516 terminates at a distal end proximate asecond subchannel 602 terminating at a first opening 606 into the fuelconduit 506. In some embodiments, the second subchannel 602 terminatesperpendicularly at the first opening 606 relative to the fuel conduit506. In some embodiments, the second airflow conduit 518 terminates at adistal end proximate a fourth subchannel 604 terminating at a secondopening 608 into the fuel conduit 506. In some embodiments, the fourthsubchannel 604 terminates perpendicularly at the second opening 608relative to the fuel conduit 506. In some embodiments, one or both ofthe second subchannel 602 and the fourth subchannel 604 terminates at anoblique-angle that allows an air stream to be discharged at an angularrange from 0 degrees to 60 degrees at its corresponding opening relativeto the fuel conduit 506 as shown in FIG. 8.

In some embodiments, the first opening 606 is configured to discharge anair stream at a third angular range 610. In some embodiments, the secondopening 608 is configured to discharge an air stream at a fourth angularrange 612. In some embodiments, the third angular range 610 and thefourth angular range 612 are substantially the same. In someembodiments, the third angular range 610 is different and/or distinctfrom the fourth angular range 612. In some embodiments, the thirdangular range 610 and/or the fourth angular range 612 comprise anangular range from 0 degrees to 60 degrees, where 0 degrees isperpendicular relative to the fuel conduit 506. The angular range ismeasured between 0 degrees and 60 degrees. In some embodiments, thefirst opening 606 and the second opening 608 are shaped, sized, and/orconfigured to have a particular angular range 610, 612 to achieve apredetermined and/or desired fuel zone coverage, dispersion, and/oratomization of the fuel. In some embodiments, the first opening 606 intothe fuel conduit 506 is positioned substantially horizontally acrossfrom the second opening 608 into the fuel conduit 506.

In some embodiments, the corresponding one or more air orifices pairedwith the fuel window 520 are defined in one or more gaps formed betweenthe heat shield wall 406 and the spray bar 502 as shown in FIG. 7. FIG.7 is a cross-sectional view of an exemplary paired fuel window-airorifices 202 of an exemplary fuel spray apparatus 102 in accordance withsome embodiments. In some embodiments, the heat shield wall 406 at leastpartially surrounds the spray bar 502 proximate to the fuel injectionaperture 504. In some embodiments, the air from the main airflow conduit402 is directed to flow into an upstream gap 702 and a downstream gap704 terminating at the fuel conduit 506. In some embodiments, theupstream gap 702 and the downstream gap 704 are formed between the heatshield wall 406 and the spray bar 502 to direct the air that flowsthrough these gaps to cooperatively impinge the fuel jet into a shape asthe fuel jet comes out of the fuel injection aperture 504 to the fuelconduit 506 and out of the fuel window 520. In some embodiments, the fanair/bypass air 208 directed through the upstream gap 702 and thedownstream gap 704 forms an air curtain exiting the fuel window 520 toshield the fuel jet from the core exhaust flow 104.

In some embodiments, the corresponding one or more air orifices pairedwith the fuel window 520 includes one or more combination of airorifices shown and/or described in FIGS. 5-7. In an illustrativenon-limiting embodiment, the corresponding one or more air orificespaired with the fuel window 520 may be as shown and/or described in FIG.8. FIG. 8 is a cross-sectional view of an exemplary paired fuelwindow-air orifices 202 of an exemplary fuel spray apparatus 102 inaccordance with some embodiments. In some embodiments, the first airflowconduit 516 splits into a first subchannel 802 and the second subchannel602. In some embodiments, the first orifice 508 is located at a terminalend of the first subchannel 802 and the second subchannel 602 terminatesat the first opening 606 into the fuel conduit 506. In some embodiments,the second airflow conduit 518 splits into a third subchannel 804 andthe fourth subchannel 604. In some embodiments, the second orifice 510is located at a terminal end of the third subchannel 804 and the fourthsubchannel 604 terminates at the second opening 608 into the fuelconduit 506. In some embodiments, a centerline of the first subchannel802 is at an oblique-angle relative to the second centerline 526 of thefuel conduit 506. In some embodiments, a centerline of the thirdsubchannel 804 is parallel relative to the second centerline 526 of thefuel conduit 506. In some embodiments, a centerline of the thirdsubchannel 804 is parallel to the second centerline 526 of the fuelconduit 506.

To further illustrate, FIG. 8 is described along with an exemplaryprocess/method 1300 shown in FIG. 13. FIG. 13 shows a flow diagram ofthe exemplary process/method 1300 of spraying fuel in an augmented gasturbine engine 100 in accordance with some embodiments. In someembodiments, the exemplary process/method 1300 is applicable to thepaired fuel window-air orifices 202 and/or the fuel spray apparatus 102shown and/or described in FIGS. 1-12. In some embodiments, the method1300 includes directing a fuel jet 810 into the core exhaust flow 104 ofan augmented gas turbine engine 100 via a fuel window 520 of the fuelconduit 506 configured to receive the fuel jet 810 from the fuelinjection aperture 504 of the spray bar 502, at step 1302. In someembodiments, the method 1300 includes directing a first air stream 806into the core exhaust flow 104 via the first orifice 508, at step 1304.In some embodiments, the main airflow conduit 402 directs the fanair/bypass air 208 to the first airflow conduit 516. In someembodiments, the first subchannel 802 directs portions of the fanair/bypass air 208 out of the first orifice 508 and discharges the firstair stream 806 into the core exhaust flow 104. In some embodiments, thefirst air stream 806 shapes and/or steers downwardly the fuel jet 810,thereby controlling the fuel zone coverage, dispersion, and/oratomization of the fuel in the augmented gas turbine engine 100. In someembodiments, the first air stream 806 shields the fuel jet 810 flow fromhigh momentum core flow (e.g., the core exhaust flow 104) to improvefuel penetration into the core of the augmented gas turbine engine 100.In some embodiments, the method 1300 includes directing a third airstream via the second subchannel 602 of the first airflow conduit 516through the first opening 606 into the fuel conduit 506. In someembodiments, the third air stream impinges on the fuel jet 810 as thefuel jet 810 comes out of the fuel injection aperture 504. In someembodiments, the third air stream further shapes the upstream side ofthe fuel jet 810.

In some embodiments, the method 1300 includes directing a second airstream 808 into the core exhaust flow 104 via the second orifice 510, atstep 1306. In some embodiments, the main airflow conduit 402 directs thefan air/bypass air 208 to the second airflow conduit 518. In someembodiments, the third subchannel 804 directs portions of the fanair/bypass air 208 out of the second orifice 510 and discharges thesecond air stream 808 into the core exhaust flow 104. In someembodiments, the second air stream 808 shapes the fuel jet 810 tocontrol the fuel zone coverage, dispersion, and/or atomization of thefuel in the augmented gas turbine engine 100. In some embodiments, thesecond air stream 808 builds a film layer that cools the componentsurface of the fuel spray apparatus 102. In some embodiments, the secondair stream 808 provides an air buffer from the fuel sprayed into thefreestream and/or the core exhaust flow 104 to abate against distressthat generally results from fuel wetting of the component surface andtemperature magnitude or gradient.

In some embodiments, the method 1300 includes directing a fourth airstream via the fourth subchannel 604 of the second airflow conduit 518through the second opening 608 into the fuel conduit 506 to additionallyimpinge on the fuel jet 810 as the fuel jet 810 comes out of the fuelinjection aperture 504. In some embodiments, the method 1300 includesdirecting at least one of the fan air/bypass air 208 or bleed air of theaugmented gas turbine engine 100 into the first airflow conduit 516 andthe second airflow conduit 518. In some embodiments, the method 1300includes directing the fan air/bypass air 208 to flow into the upstreamgap 702 and/or downstream gap 704. In some embodiments, the upstream gap702 and the downstream gap 704 are formed between the heat shield wall406 and the spray bar 502 to cooperatively impinge the fuel jet 810 intoa shape as the fuel jet 810 comes out of the fuel window 520. In someembodiments, the main airflow conduit 402 directs the fan air/bypass air208 into the first airflow conduit 516 and the second airflow conduit518.

FIG. 9 is a top-down view illustration of an exemplary fuel sprayapparatus 102 in accordance with some embodiments. In some embodiments,the fuel spray apparatus 102 includes a plurality of paired fuelwindow-air orifices 202. In some embodiments, each of a first pairedfuel window-air orifices 902, a second paired fuel window-air orifices904, a third paired fuel window-air orifices 906, and a fourth pairedfuel window-air orifices 908 are variously and/or distinctly configuredrelative to the others based at least on a predetermined and/or desiredfuel zone coverage, dispersion, and/or atomization of the fuel.Variation in each of the plurality of paired fuel window-air orifices202 can be based on radial groupings, axial groupings, and/or for everyair orifice and/or on each design parameter (e.g., directionality,shape, and/or size of air orifices, to name a few, as described herein)of the paired fuel window-air orifices 202. In some embodiments, each ofthe plurality of paired fuel window-air orifices 202 can be particularlyoptimized for corresponding fuel window throughout the radial length ofthe fuel spray apparatus 102. In some embodiments, each orifice of apaired fuel window-air orifices 202 can be offset from the correspondingfuel window to align with the core exhaust flow 104 and/or core flowstreamlines. In some embodiments, pairing of a particularly configuredair orifices with a particular fuel window for spraying fuel in anaugmented gas turbine engine as described herein improves flame holdingcapability, combustion dynamics, and/or heat release distribution.

In an illustrative non-limiting example, the second orifice 510associated with the first paired fuel window-air orifices 902 is of acircular shape while the first orifice 508 associated with the secondpaired fuel window-air orifices 904 is of a square shape. In anotherillustrative non-limiting example, the first orifice 508 and the secondorifice 510 associated with the third paired fuel window-air orifices906 are both of a circular shape while the first orifice 508 and thesecond orifice 510 associated with the fourth paired fuel window-airorifices 908 may both of an oblong shape. In some embodiments, eachpaired fuel window-air orifices 202 on a first side of the fuel sprayapparatus 102 is paired with substantially similarly configured pairedfuel window-air orifices 202 on an opposite to the first side of thefuel spray apparatus 102 as shown in FIG. 9.

In some embodiments, the plurality of paired fuel window-air orifices202 are arranged in a fuel spray bar configuration for spraying fuelwithin the augmentor portion 106. In an illustrative non-limitingexample, the first paired fuel window-air orifices 902 includes a spraybar 502 with a fuel injection aperture 504 to inject a first fuel jetinto a first fuel conduit 506. In some embodiments, the first pairedfuel window-air orifices 902 includes the first fuel conduit 506 havinga fuel window 520 to discharge the first fuel jet into a core exhaustflow 104 in the augmentor portion 106. In some embodiments, the firstpaired fuel window-air orifices 902 includes a first airflow conduit 516having a first orifice 508 to discharge a first air stream 806 into thecore exhaust flow 104. In some embodiments, the first paired fuelwindow-air orifices 902 includes a second airflow conduit 518 having asecond orifice 510 to discharge a second air stream 808 into the coreexhaust flow 104. The first orifice 508 and the second orifice 510 arepaired with the fuel window 520 to cooperatively shape the first fueljet coming out of the fuel window 520. In some embodiments, the firstorifice 508 is a first distance 910 relative to the fuel window 520while the second orifice 510 is a second distance 912 relative to thefuel window 520. In some embodiments, the first orifice 508 is locatedon an upstream side of the fuel window 520 relative to the core exhaustflow 104. In some embodiments, the second orifice 510 is located on adownstream side of the fuel window 520 relative to the core exhaust flow104.

In another illustrative non-limiting example, the second paired fuelwindow-air orifices 904 includes a spray bar 502 with a fuel injectionaperture 504 to inject a second fuel jet into a fuel conduit 506. Insome embodiments, the fuel conduit 506 having a fuel window 520 todischarge the second fuel jet into the core exhaust flow 104. In someembodiments, a first airflow conduit 516 having a first orifice 508 todischarge a third air stream into the core exhaust flow 104 and a secondairflow conduit 518 having a second orifice 510 to discharge a fourthair stream into the core exhaust flow 104. In some embodiments, thefirst orifice 508 and the second orifice 510 are paired with the fuelwindow 520 to cooperatively shape the second fuel jet coming out of thefuel window 520. In some embodiments, the first orifice 508 is a thirddistance 914 relative to the fuel window 520 while the second orifice510 is a fourth distance 916 relative to the fuel window 520.

In another illustrative non-limiting example, the first orifice 508 ofthe second paired fuel window-air orifices 904 is adjacent to the secondorifice 510 of the first paired fuel window-air orifices 902. In someembodiments, the second orifice 510 of the first paired fuel window-airorifices 902 may be configured to discharge the second air stream 808 ata first angular range and the first orifice 508 of the second pairedfuel window-air orifices 904 may be configured to discharge the thirdair stream 806 at a second angular range different from the firstangular range. In another illustrative non-limiting example, a firstshape of the second orifice 510 of the first paired fuel window-airorifices 902 is distinct from a second shape of the first orifice 508 ofthe second paired fuel window-air orifices 904.

FIG. 10 is a simplified illustration of an exemplary fuel sprayapparatus 1000 in accordance with some embodiments. In some embodiments,the fuel spray apparatus 1000 includes one or more paired fuelwindow-air orifices 202. In some embodiments, the fuel spray apparatus1000 includes a heat shield body 210 integrated with the one or morepaired fuel window-air orifices 202. In some embodiments, the fuel sprayapparatus 1000 includes one or more fuel spray inlets 114 to receivefuel discharged by the one or more paired fuel window-air orifices 202.In some embodiments, a portion of the fuel spray apparatus 1000 isenclosed in the fan duct 108. In some embodiments, the portion of thefuel spray apparatus 1000 enclosed in the fan duct 108 includes at leastone fan duct inlet 1010 to receive fan air/bypass air 208. In someembodiments, portions of the fan air/bypass air 208 flowing in the fanduct 108 enters the at least one fan duct inlet 1010 while the remainingportions of the fan air/bypass air 208 flows around/bypasses the fanduct-enclosed portion of the fuel spray apparatus 102 to continuedownstream of the fan duct 108. In some embodiments, the fuel sprayapparatus 1000 is secured to the fan duct 108 with one or more fasteners206. In some embodiments, the fuel spray apparatus 1000 includes a bleedair supply pipe 1004, a bleed air manifold 1006, and/or one or morecontrol valves 1008. In some embodiments, the bleed air supply pipe 1004receives bleed air 1002 sourced from a compressor bleed offtake and/orelsewhere on the augmented gas turbine engine 100. In some embodiments,the bleed air from the bleed air supply pipe 1004 enters the bleed airmanifold 1006 and individually directs air to each bleed air conduit1102. The fan air/bypass air 208 flowing inside the fan duct 108 andportions of the one or more fuel spray inlets 114 and the bleed airsupply pipe 1004 shown inside the fan duct 108 are depicted as visiblein FIG. 10 for illustration purposes. They are enclosed by the heatshield body 210 and generally not visible. Portions of the fuel sprayapparatus 1000 including the at least one fan duct inlet 1010 that areenclosed inside the fan duct 108 are depicted as visible in FIG. 10 forillustration purposes. Once the fuel spray apparatus 102 is fastened tothe fan duct 108, this portion of the fuel spray apparatus 102 isgenerally not visible.

To further illustrate, another illustrative non-limiting examples of oneor more paired fuel window-air orifices are shown and described in FIGS.11 and 10. FIG. 11 is a schematic illustration of a cross-section of theexemplary fuel spray apparatus 1000 of FIG. 10 showing layers ofconduits and heat shield walls arrangements 1100 in accordance with someembodiments. FIG. 12 is a cross-sectional view of two exemplary pairedfuel window-air orifices 1200 of an exemplary fuel spray apparatus 1000,in accordance with some embodiments. In some embodiments, a distinctionbetween the fuel spray apparatus 102 previously described above and thefuel spray apparatus 1000 described below is the alternative source ofair supplying the first airflow conduit 516, the second airflow conduit518, the first subchannel 802, the third subchannel 804, the secondsubchannel 602, and/or the fourth subchannel 604.

In FIG. 11, a heat shield external wall 1104 is a top layer forming asurface and/or the heat shield body 210 of the fuel spray apparatus1000. In some embodiments, the heat shield external wall 1104 providesprotection/shielding to spray bars 502 of FIG. 12 from the temperatureenvironment inside the augmented gas turbine engine 100. In someembodiments, the main airflow conduit 402 directs the fan air/bypass air208 to at least partially surround a spray bar 502 of FIG. 10. In someembodiments, the spray bar 502 directs fuel to the one or more fuelapertures 504 of the fuel spray apparatus 1000. In some embodiments, theat least one fan duct inlet 1010 of FIG. 10 is an opening to the mainairflow conduit 402 that receives the fan air/bypass air 208 from thefan duct 108.

In some embodiments, the air from the main airflow conduit 402 isdirected to flow into an upstream gap 702 and a downstream gap 704terminating at the fuel conduit 506. In some embodiments, the upstreamgap 702 and the downstream gap 704 are formed between a heat shieldinternal wall 1106 and the spray bar 502 to direct the air that flowsthrough these gaps to cooperatively impinge the fuel jet into a shape asthe fuel jet comes out of the fuel injection aperture 504 to the fuelconduit 506 and out of the fuel window 520. In some embodiments, thefirst airflow conduit 516, the second subchannel 602, and the firstsubchannel 802 are grown within the heat shield internal wall 1106 andthe heat shield external wall 1104 using 3D printing or additivemanufacturing process. In some embodiments, the third subchannel 804,the fourth subchannel 604, and the second airflow conduit 518 are grownwithin the heat shield internal wall 1106 and the heat shield externalwall 1104 using 3D printing or additive manufacturing process. In someembodiments, the bleed air flowing through the one or more controlvalves 1008 supplies each of the first airflow conduit 516, the secondsubchannel 602, the first subchannel 802, the third subchannel 804, thefourth subchannel 604, and the second airflow conduit 518 via the bleedair conduit 1102.

In some embodiments, the third subchannel 804 includes an obliquesubchannel portion 1202 and a parallel subchannel portion 1204. In someembodiments, a centerline of the oblique subchannel portion 1202 is atan oblique angle relative to the second centerline 526 of the fuelconduit 506. In some embodiments, the oblique subchannel portion 1202terminates at a distal end 1206 of the parallel subchannel portion 1204.In some embodiments, the parallel subchannel portion 1204 terminates atthe second orifice 510. In some embodiments, a centerline of theparallel subchannel portion 1204 is parallel relative to the secondcenterline 526 of the fuel conduit 506.

The inventive subject matter is not limited to the specific aspectsdescribed and illustrated herein. Different aspects and adaptationsbesides those shown herein and described, as well as many variations,modifications and equivalent arrangements will now be apparent or willbe reasonably suggested by the foregoing specification and drawings,without departing from the substance or scope of the inventive subjectmatter.

This written description uses examples to describe aspects of thedisclosure described herein, including the best mode, and also to enableany person skilled in the art to practice aspects of the disclosure,including making and using any devices or systems and performing anyincorporated methods.

Further aspects of the disclosure are provided by the subject matter ofthe following clauses:

A fuel spray apparatus for spraying fuel in an augmented gas turbineengine including a spray bar with a fuel injection aperture to inject afuel jet into a fuel conduit, the fuel conduit having a fuel window todischarge the fuel jet into a core exhaust flow of an augmented gasturbine engine, a first airflow conduit having a first orifice todischarge a first air stream into the core exhaust flow, and a secondairflow conduit having a second orifice to discharge a second air streaminto the core exhaust flow, wherein the first orifice and the secondorifice are paired with the fuel window to cooperatively shape the fueljet coming out of the fuel window.

The fuel spray apparatus of any preceding clause further includes asecond spray bar with a second fuel injection aperture to inject asecond fuel jet into a second fuel conduit, the second fuel conduithaving a second fuel window to discharge the second fuel jet into thecore exhaust flow, a third airflow conduit having a third orifice todischarge a third air stream into the core exhaust flow, and a fourthairflow conduit having a fourth orifice to discharge a fourth air streaminto the core exhaust flow, wherein the third orifice and the fourthorifice are paired with the second fuel window to cooperatively shapethe second fuel jet coming out of the second fuel window, wherein thefirst orifice is a first distance relative to the fuel window and thesecond orifice is a second distance relative to the fuel window, andwherein the third orifice is a third distance relative to the secondfuel window and the second orifice is a fourth distance relative to thesecond fuel window.

The fuel spray apparatus of any preceding clause wherein the firstairflow conduit splits into a first subchannel and a second subchannel,and wherein the first orifice is located at a terminal end of the firstsubchannel and the second subchannel terminates at a first opening intothe fuel conduit.

The fuel spray apparatus of any preceding clause wherein the secondairflow conduit splits into a third subchannel and a fourth subchannel,wherein the second orifice is located at a terminal end of the thirdsubchannel and the fourth subchannel terminates at a second opening intothe fuel conduit.

The fuel spray apparatus of any preceding clause wherein the firstopening into the fuel conduit is positioned substantially horizontallyacross the second opening into the fuel conduit.

The fuel spray apparatus of any preceding clause wherein a firstcenterline of the first airflow conduit is at a first angle relative toa second centerline of the fuel conduit, and wherein a third centerlineof the second airflow conduit is at a second angle relative to thesecond centerline of the fuel conduit.

The fuel spray apparatus of any preceding clause further including amain airflow conduit to direct air into the first airflow conduit andthe second airflow conduit, and a heat shield wall at least partiallysurrounding the spray bar proximate the fuel injection aperture, whereinthe air is directed to flow into a gap between the heat shield wall andthe spray bar to cooperatively impinge the fuel jet into the shape asthe fuel jet comes out of the fuel window and form an air curtain toshield the fuel jet from the core exhaust flow.

The fuel spray apparatus of any preceding clause wherein at least one ofa first shape of the first orifice or a second shape of the secondorifice comprises a circular shape.

The fuel spray apparatus of any preceding clause wherein the fuel windowis approximately equidistant from both the first orifice and the secondorifice.

The fuel spray apparatus of any preceding clause wherein the firstorifice is positioned substantially across the second orifice relativeto the fuel window.

The fuel spray apparatus of any preceding clause wherein the firstairflow conduit and the second airflow conduit are configured to receiveat least one of bypass air and bleed air of the augmented gas turbineengine.

A system for spraying fuel in an augmented gas turbine engine, thesystem including a gas turbine engine having an augmentor portion forburning fuel, and at least one fuel spray bar for spraying fuel withinthe augmentor portion, the at least one fuel spray bar including a firstspray bar with a fuel injection aperture to inject a first fuel jet intoa first fuel conduit, the first fuel conduit having a first fuel windowto discharge the first fuel jet into a core exhaust flow of theaugmentor portion, a first airflow conduit having a first orifice todischarge a first air stream into the core exhaust flow, and a secondairflow conduit having a second orifice to discharge a second air streaminto the core exhaust flow, wherein the first orifice and the secondorifice are paired with the first fuel window to cooperatively shape thefirst fuel jet coming out of the first fuel window.

The fuel spray apparatus of any preceding clause wherein the at leastone fuel spray bar further including a second spray bar with a secondfuel injection aperture to inject a second fuel jet into a second fuelconduit, the second fuel conduit having a second fuel window todischarge the second fuel jet into the core exhaust flow, a thirdairflow conduit having a third orifice to discharge a third air streaminto the core exhaust flow, and a fourth airflow conduit having a fourthorifice to discharge a fourth air stream into the core exhaust flow,wherein the third orifice and the fourth orifice are paired with thesecond fuel window to cooperatively shape the second fuel jet coming outof the second fuel window, wherein the first orifice is a first distancerelative to the fuel window and the second orifice is a second distancerelative to the fuel window, and wherein the third orifice is a thirddistance relative to the second fuel window and the second orifice is afourth distance relative to the second fuel window.

The fuel spray apparatus of any preceding clause wherein the thirdorifice is adjacent to the second orifice, the second orifice configuredto discharge the second air stream at a first angular range and thethird orifice configured to discharge the third air stream at a secondangular range different from the first angular range.

The fuel spray apparatus of any preceding clause wherein the thirdorifice is adjacent to the second orifice, and wherein a first shape ofthe second orifice is distinct from a second shape of the third orifice.

The fuel spray apparatus of any preceding clause wherein the firstorifice is located on an upstream side of the fuel window relative tothe core exhaust flow, and wherein the second orifice is located on adownstream side of the fuel window relative to the core exhaust flow.

A method for spraying fuel in an augmented gas turbine engine includingdirecting a fuel jet into a core exhaust flow of an augmented gasturbine engine via a fuel window of a fuel conduit configured to receivethe fuel jet from a fuel injection aperture of a spray bar, directing afirst air stream into the core exhaust flow via a first orifice of afirst airflow conduit, and directing a second air stream into the coreexhaust flow via a second orifice of a second airflow conduit, whereinthe first air stream and the second air stream cooperatively impinge thefuel jet into a shape as the fuel jet comes out of the fuel window.

The fuel spray apparatus of any preceding clause further includingdirecting a third air stream via a subchannel of the first airflowconduit through a first opening into the fuel conduit to impinge on thefuel jet as the fuel jet comes out of the fuel injection aperture.

The fuel spray apparatus of any preceding clause further includingdirecting a fourth air stream via a subchannel of the second airflowconduit through a second opening into the fuel conduit to additionallyimpinge on the fuel jet as the fuel jet comes out of the fuel injectionaperture.

The fuel spray apparatus of any preceding clause further includingdirecting at least one of bypass air or bleed air of the augmented gasturbine engine into the first airflow conduit and the second airflowconduit.

What is claimed is:
 1. A fuel spray apparatus for spraying fuel in anaugmented gas turbine engine, the fuel spray apparatus comprising: aspray bar with a fuel injection aperture configured to inject a fuel jetinto a fuel conduit; the fuel conduit having a fuel window to dischargethe fuel jet into a core exhaust flow of the augmented gas turbineengine; a first channel directing a first air stream into the fuelconduit; and a second channel directing a second air stream into thefuel conduit, wherein the first air stream and the second air streamcooperatively shape the fuel jet coming out of the fuel window.
 2. Thefuel spray apparatus of claim 1, wherein the first channel correspondsto a first airflow conduit having a first orifice that discharges thefirst air stream into the fuel conduit, and wherein the second channelcorresponds to a second airflow conduit having a second orifice thatdischarges the second air stream into the fuel conduit.
 3. The fuelspray apparatus of claim 2, wherein the first orifice is positionedsubstantially horizontally across the second orifice.
 4. The fuel sprayapparatus of claim 1, wherein a first centerline of the first channel isat a first angle relative to a second centerline of the fuel conduit,and wherein a third centerline of the second channel is at a secondangle relative to the second centerline of the fuel conduit.
 5. The fuelspray apparatus of claim 1, further comprising: a main airflow conduitto direct air into the first channel and the second channel; and a heatshield wall at least partially surrounding the spray bar proximate thefuel injection aperture, wherein the air is directed to flow into a gapbetween the heat shield wall and the spray bar to cooperatively impingethe fuel jet into the shape as the fuel jet comes out of the fuel windowand form an air curtain to shield the fuel jet from the core exhaustflow.
 6. The fuel spray apparatus of claim 1, wherein the first channeland the second channel are configured to receive at least one of bypassair or bleed air of the augmented gas turbine engine.
 7. The fuel sprayapparatus of claim 1, wherein the first channel corresponds to a firstgap formed between a heat shield wall and the spray bar, and wherein thesecond channel corresponds to a second gap formed between the heatshield wall and the spray bar.
 8. The fuel spray apparatus of claim 1,further comprising: a first airflow conduit having a first orifice todischarge a third air stream into the core exhaust flow; and a secondairflow conduit having a second orifice to discharge a fourth air streaminto the core exhaust flow, wherein the first orifice and the secondorifice are paired with the fuel window to cooperatively shape the fueljet coming out of the fuel window.
 9. The fuel spray apparatus of claim8, wherein the first orifice is positioned substantially across thesecond orifice relative to the fuel window.
 10. The fuel spray apparatusof claim 8, wherein at least one of a first shape of the first orificeor a second shape of the second orifice comprises a circular shape. 11.The fuel spray apparatus of claim 8, wherein the fuel window isapproximately equidistant from both the first orifice and the secondorifice.
 12. The fuel spray apparatus of claim 1, wherein the firstchannel and the second channel are paired with the fuel window tocooperatively shape the fuel jet coming out of the fuel window.
 13. Thefuel spray apparatus of claim 1, further comprising: a second spray barwith a second fuel injection aperture to inject a second fuel jet into asecond fuel conduit; the second fuel conduit having a second fuel windowto discharge the second fuel jet into the core exhaust flow; a thirdchannel directing a third air stream into the second fuel conduit; and afourth channel directing a fourth air stream into the second fuelconduit, wherein the third channel and the fourth channel are pairedwith the second fuel window to cooperatively shape the second fuel jetcoming out of the second fuel window.
 14. A system for spraying fuel inan augmented gas turbine engine, the system comprising: a gas turbineengine having an augmentor portion for burning the fuel; and at leastone fuel spray bar for spraying the fuel within the augmentor portion,the at least one fuel spray bar comprising: a first spray bar with afuel injection aperture to inject a fuel jet into a fuel conduit; thefuel conduit having a fuel window to discharge the fuel jet into a coreexhaust flow of the augmented gas turbine engine; a first channeldirecting a first air stream into the fuel conduit; and a second channeldirecting a second air stream into the fuel conduit, wherein the firstair stream and the second air stream cooperatively shape the fuel jetcoming out of the fuel window.
 15. The system of claim 14, wherein theat least one fuel spray bar further comprises: a second spray bar with asecond fuel injection aperture to inject a second fuel jet into a secondfuel conduit; the second fuel conduit having a second fuel window todischarge the second fuel jet into the core exhaust flow; a thirdchannel directing a third air stream into the second fuel conduit; and afourth channel directing a fourth air stream into the second fuelconduit, wherein the third channel and the fourth channel are pairedwith the second fuel window to cooperatively shape the second fuel jetcoming out of the second fuel window.
 16. The system of claim 14,wherein the first channel is adjacent to the second channel, the secondchannel configured to discharge the second air stream at a first angularrange and the first channel configured to discharge the first air streamat a second angular range different from the first angular range. 17.The system of claim 14, wherein the first channel corresponds to a firstairflow conduit having a first orifice that discharges the first airstream into the fuel conduit, and wherein the second channel correspondsto a second airflow conduit having a second orifice that discharges thesecond air stream into the fuel conduit.
 18. The system of claim 14,wherein the first channel and the second channel are paired with thefuel window to cooperatively shape the fuel jet coming out of the fuelwindow.
 19. The system of claim 14, wherein the first channelcorresponds to a first gap formed between a heat shield wall and the atleast one fuel spray bar, and wherein the second channel corresponds toa second gap formed between the heat shield wall and the at least onefuel spray bar.
 20. A method for spraying fuel in an augmented gasturbine engine comprising: directing a fuel jet into a core exhaust flowof the augmented gas turbine engine via a fuel window of a fuel conduitconfigured to receive the fuel jet from a fuel injection aperture of aspray bar; directing a first air stream into the fuel conduit; anddirecting a second air stream into the fuel conduit, wherein the firstair stream and the second air stream cooperatively shape the fuel jetcoming out of the fuel window.